Minimally intrusive and nonintrusive supersonic injectors for LANTR and RBCC/Scramjet propulsion systems

Abstract

A family of supersonic injectors for use on spaceplanes, rockets and missiles and the like is disclosed and claimed. Each injector maintains a specific constant (uniform) Mach number along its length when used while being minimally intrusive at significantly higher injectant pressure than combustor freestream total pressure. Each injector is substantially non-intrusive when it is not being used. The injectors may be used individually or in a group. Different orientations of the injectors in a group promotes greater penetration and mixing of fuel or oxidizer into a supersonic combustor. The injectors can be made from single piece of Aluminum, investment cast metal, or ceramic or they can be made from starboard and port blocks strapped together to accurately control the throat area. Each injector includes an elongated body having an opening which in cross section is an hour glass (venturi shaped) and the opening diverges in width and depth from the bow section to the stem section of the opening.

We claim:  
     
       1. A fuel injector comprising: an elongated body; said elongated body having an opening therein; and, said opening having a substantially hour-glass shape in cross section. 
     
     
       2. A fuel injector as claimed in  claim 1  wherein said elongated body further includes a bow section and a stern section and said opening having a substantially hour-glass shape in cross section extends from said bow section to said stern section. 
     
     
       3. A fuel injector as claimed in  claim 2  wherein said opening having a substantially hour-glass shape in cross section has a width and said width diverges from said bow section to said stern section. 
     
     
       4. A fuel injector as claimed in  claim 3  wherein said opening having a substantially hour-glass shape in cross section has a depth and said depth diverges from said bow section to said stern section. 
     
     
       5. A fuel injector as claimed in  claim 4  wherein said elongated body comprises a port half and a starboard half and said opening having a substantially hour-glass shape in cross section includes a throat area which diverges from said bow section to said stern section. 
     
     
       6. A fuel injector as claimed in  claim 5  further comprising a first strap and a second strap, said first strap affixed to said bow section of said injector and said second strap affixed to said stern section of said injector, said first and second straps space said port and starboard halfs apart so as to control said throat area and to slightly vary the specific injectant velocity from said opening having a substantially hour-glass shape in cross section. 
     
     
       7. A fuel injector as claimed in  claim 1  wherein said elongated body is comprised of 2124 Aluminum. 
     
     
       8. A fuel injector as claimed in  claim 1  wherein said elongated body includes a concave surface. 
     
     
       9. A fuel injector as claimed in  claim 1  wherein said elongated body includes a convex surface. 
     
     
       10. A fuel injector as claimed in  claim 1  wherein said elongated body includes a curved opening. 
     
     
       11. A fuel injector as claimed in  claim 1  wherein said elongated body includes a concave surface. 
     
     
       12. A fuel injector as claimed in  claim 1  wherein said elongated body includes a convex surface. 
     
     
       13. A fuel injector as claimed in  claim 2  wherein said stern section of said elongated body includes a stern wall; and, said stern wall being angled in the direction of the flow of the combustion air so as to substantially eliminate any disturbance of said injector when not in use. 
     
     
       14. A fuel injector for a combustor comprising: an elongated body; said elongated body being flush mounted to said combustor; said elongated body having an opening therein; and, said opening having a substantially venturi shape in cross section. 
     
     
       15. A fuel injector for a combustor as claimed in  claim 14  wherein said elongated body further includes a bow section and a stern section and said opening having a substantially venturi shape in cross section extends from said bow section to said stern section. 
     
     
       16. A fuel injector for a combustor as claimed in  claim 15  wherein said opening having a substantially venturi shape has a width and said width diverges from said bow section to said stern section. 
     
     
       17. A fuel injector for a combustor as claimed in  claim 16  wherein said opening having a substantially venturi shape opening has a depth and said depth diverges from said bow section to said stern section. 
     
     
       18. A fuel injector for a combustor as claimed in  claim 17  wherein said elongated body comprises a port half and a starboard half and said opening having a substantially venturi shape in cross section includes a throat area which diverges from said bow section to said stern section. 
     
     
       19. A fuel injector for a combustor as claimed in  claim 18  further comprising a first strap and a second strap, said first strap affixed to said bow section of said injector and said second strap affixed to said stern section of said injector, said first and second straps space said port and starboard halves apart so as to control said throat area and to slightly vary the specific uniform injectant velocity from said opening having a substantially venturi shape in cross section. 
     
     
       20. A fuel injector for a combustor as claimed in  claim 14  wherein said elongated body is selected from the group of 2124 Aluminum, investment cast metal, vapor deposited metal or ceramics. 
     
     
       21. A fuel injector for a combustor as claimed in  claim 14  wherein said elongated body includes a concave surface. 
     
     
       22. A fuel injector for a combustor as claimed in  claim 14  wherein said elongated body includes a convex surface. 
     
     
       23. A fuel injector for a combustor as claimed in  claim 14  wherein said elongated body includes a curved opening. 
     
     
       24. A fuel injector flush mounted in a combustor comprising an elongated body having proximate and distal portions; said elongated body includes an opening having a substantially hour-glass shape in cross section; said opening includes a width and a depth; and, said width and depth of said opening increases from said proximate portion to said distal portion. 
     
     
       25. A fuel injector flush mounted in a combustor as claimed in  claim 24  comprising a starboard half and a port half. 
     
     
       26. A fuel injector mounted in a combustor as claimed in  claim 25  wherein said elongated body comprises a port half and a starboard half and said opening includes a throat area. 
     
     
       27. A fuel injector for a combustor as claimed in  claim 26  further comprising a first strap and a second strap, said first strap affixed to said bow section of said injector and said second strap affixed to said stern section of said injector, said first and second straps space said port and starboard halves apart so as to control said throat area of said opening and slightly vary the specific uniform injectant performance parameters of velocity, mass flow, momentum flux ratio J, plume penetration, plume width and diffusion. 
     
     
       28. A fuel injector as claimed in  claim 27  wherein said stern section of said elongated body includes a stern wall; and, said stern wall being angled in the direction of the flow of combustion air so as to substantially eliminate any disturbance of said injector when not in use. 
     
     
       29. An oxidizer or fuel injector system for injecting oxidizers or fuel into a supersonic cross flow having a specific Mach number, comprising: a plurality of Mach number specific injectors; each of said Mach number specific injectors having an elongated body having bow and stern sections; each of said elongated bodies of said Mach number specific injectors having an opening therein whose cross section is venturi shaped; each of said openings of said elongated bodies diverging from said bow to said stern; and, a selected one or a selected group of said Mach number specific injectors injecting oxidizer or fuel into said supersonic cross flow with uniform velocity from bow to stern such that the Mach number of said selected one or selected group number of said Mach number specific injectors approximately matches the Mach number of said supersonic cross flow or for specific propulsion system applications be significantly higher than the Mach number of the combustor's or rocket's supersonic cross flow.